In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are significantly important. In this study, the method of a film cooling technique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effectiveness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.
Skip Nav Destination
IbrahimH@alcor.concordia.ca
Close
Sign In or Register for Account
Article navigation
December 2011
Technical Briefs
Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow
Sung In Kim,
Sung In Kim
Department of Mechanical and Industrial Engineering,
Concordia University
, Montreal, QC, H3G 2W1, Canada
Search for other works by this author on:
Ibrahim Hassan
Ibrahim Hassan
Department of Mechanical and Industrial Engineering,
IbrahimH@alcor.concordia.ca
Concordia University
, Montreal, QC, H3G 2W1, Canada
Search for other works by this author on:
Sung In Kim
Department of Mechanical and Industrial Engineering,
Concordia University
, Montreal, QC, H3G 2W1, Canada
Ibrahim Hassan
Department of Mechanical and Industrial Engineering,
Concordia University
, Montreal, QC, H3G 2W1, Canada
IbrahimH@alcor.concordia.ca
J. Thermal Sci. Eng. Appl. Dec 2011, 3(4): 044501 (7 pages)
Published Online: October 13, 2011
Article history
Received:
December 27, 2010
Revised:
August 26, 2011
Online:
October 13, 2011
Published:
October 13, 2011
Citation
Kim, S. I., and Hassan, I. (October 13, 2011). "Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow." ASME. J. Thermal Sci. Eng. Appl. December 2011; 3(4): 044501. https://doi.org/10.1115/1.4005052
Download citation file:
- Ris (Zotero)
- Reference Manager
- EasyBib
- Bookends
- Mendeley
- Papers
- EndNote
- RefWorks
- BibTex
- ProCite
- Medlars
Close
Sign In
65
Views
0
Citations
Get Email Alerts
Cited By
Parametric study on the performance of combined power plant of steam and gas turbines
J. Thermal Sci. Eng. Appl
Control of boiling instabilities in a two-phase pumpless loop using water-alcohol mixtures
J. Thermal Sci. Eng. Appl
Related Articles
On the Use of High-Order Accurate Solutions of PNS Schemes as Basic Flows for Stability Analysis of Hypersonic Axisymmetric Flows
J. Fluids Eng (October,2007)
Waves and Compressible Flow
Appl. Mech. Rev (November,2004)
Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds
J. Heat Transfer (December,2013)
Hypersonic Flow Heat Transfer Prediction Using Single Equation Turbulence Models
J. Heat Transfer (February,2001)
Related Proceedings Papers
Related Chapters
The Development of a New Nonequilibrium Viscous Shock-Layer Technique for Computing Hypersonic Flow around Blunt_Nosed Slender Bodies
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
Human Factors Engineering and Industrial Ergonomics
An Instructional Aid For Occupational Safety and Health in Mechanical Engineering Design
An Adjustment Parameter Measuring Approach for Spacecraft Rendezvous
International Conference on Software Technology and Engineering (ICSTE 2012)